System and method of controlling the deflections of a pressure tank mounted within a vacuum tank

Patent metadata

Field	Value
Publication number	US-12325529-B2
Application number	US-202318336993-A
Country	US
Kind code	B2
Filing date	Jun 17, 2023
Priority date	Jun 17, 2023
Publication date	Jun 10, 2025
Grant date	Jun 10, 2025

Abstract

A tank system includes a vacuum tank and a pressure tank. The vacuum tank has a vacuum tank main portion extending between vacuum tank end portions. The pressure tank is mounted within the vacuum tank, and has a pressure tank main portion extending between pressure tank end portions. The tank system includes a deflection control system comprising at least one elongate support member extending from a vacuum tank first side of the vacuum tank main portion, and passing through an opening in a pressure tank first side of the pressure tank main portion, and coupled to a pressure tank second side opposite the pressure tank first side. The elongate support member is configured to support the pressure tank main portion and reduce deflections of the pressure tank main portion relative to the vacuum tank main portion when the tank system is subjected to a load.

First claim

What is claimed is:

1. A tank system, comprising:
a vacuum tank having a vacuum tank main portion extending between vacuum tank end portions;
a pressure tank mounted within the vacuum tank, and having a pressure tank main portion extending between pressure tank end portions;
a deflection control system for the pressure tank, comprising:
at least one elongate support member coupled directly to and extending from a vacuum tank wall portion at a vacuum tank first side of the vacuum tank main portion, and passing through an opening in a pressure tank first side of the pressure tank main portion and non-connected to the opening, and coupled to a pressure tank second side opposite the pressure tank first side; and
the elongate support member configured to support the pressure tank main portion and reduce deflections of the pressure tank main portion relative to the vacuum tank main portion when the tank system is subjected to a load.

2. The tank system of claim 1 , wherein:
the at least one elongate support member comprises a plurality of elongate support members extending from the vacuum tank first side to a respective plurality of wire attachment points along the pressure tank second side.

3. The tank system of claim 1 , wherein the at least one elongate support member is oriented according to one of the following:
the elongate support member is oriented vertically for counteracting a vertical load;
the elongate support member is oriented horizontally for counteracting a horizontal load.

4. The tank system of claim 1 , wherein the at least one elongate support member comprises at least one support wire.

5. The tank system of claim 4 , wherein the deflection control system further comprises:
a sleeve seal mounted in the opening in the pressure tank first side; and
a support wire sleeve extending through the sleeve seal and surrounding at least a section of the support wire located within the pressure tank and configured to reduce thermal flow into the support wire from cryogenic fluid in the pressure tank.

6. The tank system of claim 1 , wherein the deflection control system further comprises:
at least one spreader bar located within the pressure tank;
wherein the at least one elongate support member comprises:
a primary support wire coupled to the vacuum tank first side and extending through the opening in the pressure tank first side, and terminating at a distance from the spreader bar; and
a plurality of secondary support wires, each extending from the primary support wire to spaced locations along the spreader bar, and from the spreader bar to the pressure tank second side.

7. The tank system of claim 1 , wherein:
the vacuum tank wall portion comprises a vacuum tank skin having a vacuum tank inner surface;
the pressure tank main portion has a pressure tank skin having a pressure tank outer surface;
the vacuum tank skin and the pressure tank skin each have one of a scalloped cross section or a sinusoidal cross section in a longitudinal direction of the tank system, the scalloped cross section and the sinusoidal cross section each having alternating peaks and valleys; and
the vacuum tank inner surface is complementary to the pressure tank outer surface.

8. An aircraft, comprising:
a fuselage;
a tank system included with the fuselage, and comprising:
a vacuum tank having a vacuum tank main portion extending between vacuum tank end portions;
a pressure tank mounted within the vacuum tank, and having a pressure tank main portion extending between pressure tank end portions, and having a pressure tank skin having a pressure tank outer surface; and

a deflection control system for the pressure tank, comprising:
at least one elongate support member coupled directly to and extending from a vacuum tank wall portion at a vacuum tank first side of the vacuum tank main portion, and passing through an opening in a pressure tank first side of the pressure tank main portion and non-connected to the opening, and coupled to a pressure tank second side diametrically opposite the pressure tank first side; and
the elongate support member configured to support the pressure tank main portion and reduce deflections of the pressure tank main portion relative to the vacuum tank main portion when the tank system is subjected to a load.

9. The aircraft of claim 8 , wherein:
the at least one elongate support member comprises a plurality of elongate support members extending from the vacuum tank first side to a respective plurality of wire attachment points along the pressure tank second side.

10. The aircraft of claim 8 , wherein the at least one elongate support member is oriented according to one of the following:
the elongate support member is oriented vertically for counteracting a vertical load;
the elongate support member is oriented horizontally for counteracting a horizontal load.

11. The aircraft of claim 8 , wherein the at least one elongate support member comprises at least one support wire.

12. The aircraft of claim 11 , wherein the deflection control system further comprises:
a sleeve seal mounted in the opening in the pressure tank first side; and
a support wire sleeve extending through the sleeve seal and surrounding at least a section of the support wire located within the pressure tank and configured to reduce thermal flow into the support wire from cryogenic fluid in the pressure tank.

13. The aircraft of claim 8 , wherein the deflection control system further comprises:
at least one spreader bar located within the pressure tank;
wherein the at least one elongate support member comprises:
a primary support wire coupled to the vacuum tank first side and extending through the opening in the pressure tank first side, and terminating at a distance from the spreader bar; and
a plurality of secondary support wires, each extending from the primary support wire to spaced locations along the spreader bar, and from the spreader bar to the pressure tank second side.

14. The aircraft of claim 8 , wherein:
the vacuum tank wall portion comprises a vacuum tank skin having a vacuum tank inner surface;
the pressure tank main portion has a pressure tank skin having a pressure tank outer surface;
the vacuum tank skin and the pressure tank skin each have one of a scalloped cross section or a sinusoidal cross section in a longitudinal direction of the tank system, the scalloped cross section and the sinusoidal cross section each having alternating peaks and valleys; and
the vacuum tank inner surface is complementary to the pressure tank outer surface.

15. A method of reducing deflections of a pressure tank mounted within a vacuum tank of a tank system, comprising:
supporting, using at least one elongate support member of a deflection control system, a pressure tank main portion extending between pressure tank end portions of the pressure tank, from a vacuum tank main portion extending between vacuum tank end portions of the vacuum tank, in a manner such that when the tank system is subjected to a load, deflections of the pressure tank main portion relative to the vacuum tank main portion are reduced; and
wherein the at least one elongate support member is coupled directly to and extends from a vacuum tank wall portion at a vacuum tank first side of the vacuum tank main portion, and passes through an opening in a pressure tank first side of the pressure tank main portion and is non-connected to the opening, and is coupled to a pressure tank second side opposite the pressure tank first side.

16. The method of claim 15 , wherein supporting the pressure tank main porti

Assignees

• Boeing Co

Inventors

• Grip Robert E

Classifications

• F17C1/02

  involving reinforcing arrangements {(F17C1/14, F17C1/16 take precedence)} · CPC title

• F17C2270/0189

  Planes · CPC title

• F17C2203/013

  in the vessel, e.g. columns · CPC title

• F17C13/083

  for medium-sized mobile storage vessels, e.g. tank vehicles or railway tank vehicles · CPC title

• B64D37/04 Primary

  Arrangement thereof in or on aircraft · CPC title